CL605 General Knowledge Flashcards
APU battery description
24 volt, 43 amp/hour in aft equipment bay
Main Battery description
24 volt, 17 amp/hour
(605 - in nose section, 604 in rear equipment bay.)
DC Essential Bus sources of power
- Ess TRU 1
- Ess TRU 2
- APU Batt Direct Bus (DC Essential contactor)
- Main Batt Direct Bus (Emergency DC transfer contactor)
- External DC
Battery Bus sources of power
- Ess TRU 1
- Ess TRU 2
- APU Batt Direct Bus (Battery Master must be on)
- Main Batt Direct Bus (Battery Master must be on)
- External DC
DC Emer Bus - purpose and sources of power
- APU Batt Direct Bus (APU or external power)
- Battery Bus (5 sources of DC power)
- Always Powered - provides power for fire extinguishers and hydraulic shut-off valves
ADG Unit test light times
On the ground: after 2 secs, illuminates for 2 secs
In the air: after 5 secs, illuminates for 2 secs
Engine driven IDG description
IDG is a generator and a constant-speed drive combined.
Provides 115 volt AC, 400 Hz, three-phase power.
Generator control units - function
Monitors its IDG. Provides bus priority logic.
Trips-off and removes the generator from it’s AC bus if it detects:
- Over/under voltage;
- Over/under frequency;
- Gen and Bus overcurrent
AC Bus priority logic
- On-side engine-driven generator
- APU generator
- Cross-side engine-driven generator4. External AC power
ADG power decription
115 volt, 400 Hz, 15 Kva
Refueling pressure limitations
Max pressure - fuelling: 50 psi
Max defuelling pressure: -8 psi
Conditioned air distribution
Left pack: 60% cockpit, 40% cabin
Right pack: 100% cabin
Minimum taxi strip width for 180º turn with a 3 foot safety margin
61 feet
Criteria for inhibiting take-off EICAS messages
- Both engines N1 > 79%
- > 80 KIAS
- Weight on Wheels
EICAS take-off inhibit cancellation criteria
Rad alt exceeds 400 feet
Both engines N1 < 79 %
30 seconds elapsed since take-off initiated
Autopilot engagement criteria
- At least 1 yaw damper
- Both flight control computers powered on
- 1 Air Data Computer available
- No significant aircraft instability exists
Cabin altitude at which pax oxygen masks auto deploy
14,500 feet cabin alt
Vertical take-off mode initial pitch angles (TOGA button => TO TO displayed on PFD)
CL604: 12 degrees pitch up. (FlightSafety PTM 16-180 and Bombardier PTG 4-48)
CL605: 14 degrees pitch up. (Bombardier PTG 4-54)
Engine failure: 10 degrees (604 and 605)
TOGA button functions
- Disengages autopilot
- Activates vertical and lateral Go-Around mode (Generates 10 degree pitch-up command)
Oxygen low pressure EICAS message trigger pressure
825 psi
WSHLD/WIND switch functions
LOW: windshields and windows at low heat.
HI: windshields at high temp, side windows remain at low.
Ice detection probe heat cycles
Heated for 5 seconds, heat of for 55 seconds
Cowl anti-ice valves decription
Electrically controlled, pneumatically operated, pressure regulation valves. Fail safe open. Cowl anti-ice inhibited by reverser use.
Wing anti-ice valve description
Electrically controlled, pneumatically operated pressure regulating valve. Fail-safe closed.
Wing anti-ice standby mode function
Anti-ice controller by-passed. Both wing anti-ice valves controlled by their standby thermal switch.
14th stage bleed valves description
Electrically controlled, pneumatically operated, full open or closed valves. Fail safe open.
Fire bottle pressure
600-625 psiOver-pressure relief at 1400 psi
Fuel flow value at which amber dashes displayed
5000 lbs/hr or invalid data
EMER PWR ONLY EICAS message meaning
ADG powering AC essential bus. No power to AC bus 1 or 2
Minimum APU bleed air pressure for engine start
40 psi
Minimum air pressure from air start cart for engine start
45 psi
Minimum engine cross-bleed air pressure for engine start
60 psi
Power setting at which engine control switches between mechanical only and mechanical/electronic
<79 % N1 - mechanical only (FCU controls N2)>79 % N1 - FCU and electronic control (ECU controls N1)
Effect of switching ENG SPEED off
If at power settings >79 % N1, engines revert to N2 speed control. Overtemp and rapid accelerations can occur.
RPM difference at which ATS disengages
13% N1
RPM at which APR is armed during take-off
79% N1
RPM at which APR commands engines to increase N1 speed by 2 %
67.6% N1
Anti-skid operation criteria
(Armed and gear down/locked)35 knot wheel spin-upOrWOW for 5 seconds. Operational down to 10 knots wheel speed
Nominal hydraulic pressure
3000 psi
Hydraulic accumulator precharge pressure
1500 psi (nitrogen)
Pressure at which hydraulic system 3 pressure is cut-off from landing gear selector valves
2100 psi
Normal hydraulic fluid quantity
45%-85%
Maximum hydraulic fluid temperature
95ºC
WOW ground mode requirements
Any 3 of the 4 main gear prox sensors indicate weight on wheels
In case of loss of hydraulic system 2 and 3, number of brake applications available from accumulator pressure (anti-skid off)
6 applications (approx) - no anti-skid
(System 2 or 3 failure - other system anti-skid still available but only 50% braking power)
Sources of power for left and right Packs
Left pack: DC essential bus
Right pack: DC bus 2
